Section IV. LOADING LIMITS
CENTER OF GRAVITY LIMITATIONS.
Center of gravity limits and instructions for computation
of the center of gravity are contained in Chapter 6. The
center of gravity range will remain within limits,
providing the aircraft loading is accomplished according
to instructions in Chapter 6.
The ability to experience loss of
engine power and successfully stop,
continue the takeoff, or climb, before
or after gear retraction is not assured
for all conditions. Thorough mission
planning must be accomplished prior
to takeoff by analysis of maximum
takeoff weight permitted by takeoff
distance, accelerate-stop, positive
one engine inoperative climb at lift
gradient, and climb performance.
This data will describe performance
Max. Ramp Weight
Max. Takeoff Weight
Max. Landing Weight
Max. Zero Fuel Weight
The maximum weight that may be placed on the steps
of the cabin airstair door is 300 pounds.
TOILET WEIGHT LIMITATION.
The maximum weight of a person occupying the toilet
during takeoff or landing shall not exceed 238 pounds.
Section V. AIRSPEED LIMITS, MAXIMUM AND MINIMUM
All placarded airspeeds, and airspeed indicator readings
throughout this Operator's Manual are given as
indicated airspeed (IAS) unless otherwise noted.
MAXIMUM ALLOWABLE AIRSPEED.
Refer to Flight Envelope Chart (fig. 5-2) to determine
limiting airspeeds at maximum gross weight under
various conditions. The maximum allowable airspeed is
246 KIAS below 11,500 feet, and Mmo of 0.47 Mach as
indicated by the maximum allowable airspeed pointer
(red striped) between 11,500 feet to 35,000 feet.
The airspeed limit for extending the landing gear and for
flight with the landing gear extended is 178 KIAS.
LANDING GEAR RETRACTION SPEED.
The airspeed limit for retracting the landing gear is 160
WING FLAP EXTENSION SPEEDS.
The airspeed limit for APPROACH extension (40%) of
the wing flaps is 197 KIAS. The airspeed limit for full
DOWN extension (100%) of the wing flaps is 154 KIAS.
If wing flaps are extended above these speeds, the flaps
or their operating mechanisms may be damaged.
The minimum single engine control airspeed (VMCA) at
sea level standard conditions is 104 KIAS.
MAXIMUM DESIGN MANEUVERING SPEED.
The maximum design maneuvering speed is 166 KIAS.